A multi-axis amphibious copter for flying and cruising at high speeds. The multi-axis amphibious copter includes six propulsion points i.e., four propellors oriented vertically, a coaxial rotor oriented vertically, and a mini turbine thruster on the rear of the aircraft body and configured to propel the multi-axis amphibious copter forward. The multi-axis amphibious copter can land and take off vertically from congested places and can fly at cruising speeds.

A method of transporting cargo, a cargo transport system and an unmanned Wing In Ground Effect vessel (UWIG) for transporting the cargo. A wake up signal indicates assignment of a new delivery. The UWIG begins pre-flight, causes cargo to be transported to the UWIG, and causes the cargo loaded into UWIG storage compartments. Once loaded and the loaded UWIG is ready, the UWIG taxis, e.g., to the open sea. Environmentally sealed PAR thrust fans provide PAR thrust during takeoff. The UWIG flies to a delivery location where cargo is unloaded, and may be stored.

The present invention provides a morphing cross-medium unmanned craft, wherein the cross-medium unmanned craft includes a main hull, side hulls set on both sides of the main hull and a propeller; the side hulls can be flipped relative to the main hull, so that the side hulls can have different orientation attitudes relative to the main hull, which can make the unmanned craft be variant, realizing the cross-medium navigation function of high-speed flight in the air, energy-saving navigation on the surface of the water; the propeller is used to provide an appropriate power propulsion mode for the unmanned craft when the unmanned craft is in different motion states, so as to improve the matching and reliability of the power propulsion of the unmanned craft in different medium domains of water surface, underwater and air.

An attachment for an aircraft. The attachment comprises a single, central float portion positioned under a centre of the aircraft, and a retraction apparatus. One end of the retraction apparatus is attached to the float portion and another end of the retraction apparatus is attached to the underside of the aircraft. The retraction apparatus is deployable and retractable between a first and second configuration, such that, with the retraction apparatus in the first configuration, the float portion is retracted towards the aircraft fuselage and, with the retraction apparatus in the second configuration, the float portion is deployed away from the aircraft fuselage. When the float portion is deployed, the float portion allows the aircraft to land on a body of water. When the float portion is retracted, the aircraft is able to land on a ground surface. The attachment can be retrofit to an existing non-amphibious aircraft.

A seaplane float propulsion system that is configured to provide maneuverability and directional movement of a seaplane subsequent the engine and propeller being deactivated. The present invention includes a first float member and a second float member wherein the first float member includes a first propulsion assembly mounted therein and the second float member includes a second propulsion assembly mounted therein. The first propulsion assembly and second propulsion assembly are identically constructed. The propulsion assemblies are independently controlled so as to provide both directional and rotational movement of the seaplane to which the present invention is operably installed. The propulsion assemblies include elements that are operable to intake and direct water flow in order to create the desired movement of the seaplane in which the seaplane float propulsion system is installed. The propulsion assemblies include an intake element that provides ideal fluid and aero dynamics.

A craft comprises at least one hull, a main wing coupled to the hull and configured to facilitate airborne operations of the craft, a plurality of propellers that include one or more electric motor propellers and one or more combustion motor propellers arranged along each of a port side and a starboard side of the main wing and configured to generate lift on the craft by blowing air over the main wing, and a control system. The control system comprises data storage having instruction code stored thereon that, when executed by one or more processors of the control system, causes the control system to: after receiving a takeoff indication, increase thrust generated by the electric motor propellers to cause the craft to transition from a hull-borne mode of operation to an airborne mode of operation, and after a thrust adjustment condition occurs, increase thrust generated by the combustion motor propellers.

The present invention comprises a system which includes a novel quick release thruster mount system using one or more removable elements allowing the thrusters to be removed quickly. The present invention also comprises a novel float compartment centric design where no wiring to the cockpit is necessary. Redundant power units are self-contained and protected. The novel design incorporates thrust force over the surface of the water rudders improving directional control. The rudder anti lift device ALPB allows the rudders to remain in the water while reverse or braking thrust is applied. Control and monitoring are done wirelessly from the safety of the cockpit reducing hazard while maneuvering to avoid prop strike hazards to pilot, persons or objects. The system offers the ability to maintain positive directional control while taxing downwind resisting the inherent weathervane forces, braking, and turning maneuvers unachievable with current methods. The system differs from any prior art due to the aft location of drive components, method for deployment, and the fact that the drive system does not mount directly to the float itself but rather the water rudders. These forces are marginal in comparison to what is needed when one takes into consideration the Moment and Arm location of the force and the smaller lightweight thrusters do more work with less effort.

An unmanned aerial system includes an unmanned aerial vehicle having a body and a primary propulsion system coupled to the body. The primary propulsion system includes at least one propeller and at least one motor coupled to the at least one propeller. The unmanned aerial system also includes a pair of landing gears coupled to the body of the unmanned aerial vehicle. Each landing gear of the pair of landing gears includes a buoyant elongated float. The unmanned aerial system also includes a SONAR device coupled to the unmanned aerial vehicle.

Embodiments disclosed provide a pump assembly including a first pump for delivering at least one fluid. The first pump may include a first inlet coupled to the first pump for delivering at least one first fluid to the first pump, a second inlet coupled to the first pump for delivering at least one second fluid to the first pump, a first discharge coupled to the first pump for delivering the at least one first fluid at a first pressure, and a second discharge coupled to the first pump for delivering the at least one second fluid at a second pressure. In some embodiments, the first discharge and the second discharge are isolated from each other.